PCOMPLS

Bulk Data Entry Defines global ply-based composite properties for continuum shell composites.

Format - Implicit


(1)	(2)	(3)	(4)	(5)	(7)
PCOMPLS	`PID`		`CORDM`	`SB`	`LAYERWISE`
	`C8`		`INT8`
	`ID1`	`MID1`	`T1`	`THETA1`
	`ID2`	`MID2`	`T2`	`THETA2`

Format - Explicit


(1)	(2)	(3)	(4)	(5)	(7)
PCOMPLS	`PID`		`CORDM`	`SB`	`LAYERWISE`
	`C8`		`INT8`
	`ID1`	`MID1`	`T1`	`THETA1`
	`ID2`	`MID2`	`T2`	`THETA2`
	`EXPLICIT`			`NIP`

Example


(1)	(2)	(3)	(4)	(5)
PCOMPLS	100
	`C8`		ASTN
	120	1	0.9	45.0
	121	2	0.6	90.0

Definitions


Field	Contents	SI Unit Example
`PID`	Unique composite property identification number. No default (Integer > 0)
`CORDM`	Identification number of the material coordinate system. Default = 0 (Integer)
`SB`	Shear stress limit of bonding material (interlaminar shear stress limit). (Real > 0.0)
`LAYERWISE`	Defines lamination theory for heat transfer. 0 Equivalent Single Layer Theory. 1 Layer-wise Theory.
`C8`	Flag indicating that the subsequent field applies to referenced CHEXA and CPENTA solid elements.
`INT8`	Integration type. ASTN (Default) Applies the Assumed Strain Enhanced Formulation. blank
`IDi`	Global Ply ID. No default (Integer > 0)
`MIDi`	Material ID for the ply defined via the previous `IDi` field. Currently MAT1, MAT9, MAT9ORT, and MATUSR materials are supported. No default (Integer > 0)
`Ti`	Defines the user-defined ply thickness of the ply specified via the `IDi` field. 6 No default (Real > 0.0)
`THETAi`	Orientation angle of the ply within the ply plane. 4 5 Default = 0.0 (Real)
`EXPLICIT`	Flag indicating that parameters for Explicit Dynamic Analysis are to follow.
`NIP`	Number of through thickness integration points. Default = 3 (1 ≤ Integer ≤ 10)

Comments

The global Ply ID should be unique with respect to other ply's on this PCOMPLS entry.
The PCOMPLS entry is only supported for first order CHEXA and CPENTA elements.
The Global Ply IDs uniquely identify ply's across all PCOMPG and PCOMPLS entries.
The thickness direction of the composite element by default starts from face G1-G2-G3-G4 to face G5-G6-G7-G8 of the solid element. Ply numbering also follows this thickness direction. This is used to only determine the direction of the local Z axis of the plies. The local Z-axis of each ply is perpendicular to the ply plane and aligned to the thickness direction. The X-axis of the coordinate system defined via CORDM (basic system, if blank) is projected onto the ply plane to determine the local X axis for the ply. The local Y-axis is then determined by the cross-product of the local X and Z axes.
The orientation angle is measured in the positive counter clockwise direction from this projected X-axis about the local Z axis of the ply.
The actual ply thicknesses depend on the actual total geometric thickness of the solid element:
$T_{a c t u a l}^{p l y_i} = T_{a c t u a l}^{e} * (\frac{T_{i}}{T_{1} + T_{2} + .... + T_{N}})$
Where,

$T_{a c t u a l}^{p l y_i}$

Actual thickness of the Ply “I”

$T_{a c t u a l}^{e}$

Actual (or geometric) thickness of the composite element

$T_{i}$

User-defined ply thicknesses via the Ti field
Setting the LAYERWISE field to 1 offers an option for through-thickness degrees of freedom. Each layer has four internal nodes, one on each face. This option offers greater accuracy but is more computationally expensive. Setting LAYERWISE option to 1 applies a piecewise linear temperature distribution through the laminate thickness. This field only applies to Heat Transfer Analysis.